Patent US1546736A successfully refreshed from Google Patents.
US4644162A
Expired / Lapsed
US
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Cooling hole inspection
Assignee: General Electric Co
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Filing: 1984-09-20
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Granted: 1987-02-17
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Expires: 2004-09-20
Abstract
Abstract In the present invention, the temperatures of cooling passages in a gas turbine engine blade are changed, as by forcing a heated gas through them. The infrared signatures of the channels are measured during the initial temperature transient of the channels and the signatures are compared with a reference. The reference may be the signature of other channels on the same blade.
Inventors
- 👤 Thomas E. Bantel
- 👤 David C. Mack
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 06:00
CPC Classifications
G; G01; G01N; G01N25/00; G01N25/72
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
39 words
A method of inspecting a channel, comprising the following steps: (a) causing the temperature of the channel to change; (b) measuring the transient of the infrared signature of the channel; and (c) comparing the measured transient with a reference.
Claim 2
Independent Claim
39 words
A method of inspecting a channel, comprising the following steps: (a) causing the temperature of the channel to change; (b) measuring the transient of the infrared signature of the channel; and (c) comparing the measured transient with a reference.
Claim 3
Independent Claim
74 words
A method of inspecting cooling channels in a gas turbine engine blade, comprising the following steps: (a) changing the temperature of the channels by forcing a gas through the channels; (b) viewing the channels with a scanning infrared radiometer and generating an image which indicates the relative intensities of black-body radiation emitted by the channels; and (c) comparing the intensities of paragraph (b) with each other during the initial temperature transient of the channels.
Claim 4
Independent Claim
74 words
A method of inspecting cooling channels in a gas turbine engine blade, comprising the following steps: (a) changing the temperature of the channels by forcing a gas through the channels; (b) viewing the channels with a scanning infrared radiometer and generating an image which indicates the relative intensities of black-body radiation emitted by the channels; and (c) comparing the intensities of paragraph (b) with each other during the initial temperature transient of the channels.
Claim 5
Independent Claim
71 words
A method of inspecting the cooling holes in a gas turbine engine blade, comprising the steps of: (a) changing the temperatures of the holes by passing air through them; (b) viewing the holes using a scanning radiometer which is responsive to radiation in approximately the 9-12 micron range; (c) deriving at least two images at different times of the holes using the radiometer; and (d) comparing the images with reference images.
Claim 6
Independent Claim
71 words
A method of inspecting the cooling holes in a gas turbine engine blade, comprising the steps of: (a) changing the temperatures of the holes by passing air through them; (b) viewing the holes using a scanning radiometer which is responsive to radiation in approximately the 9-12 micron range; (c) deriving at least two images at different times of the holes using the radiometer; and (d) comparing the images with reference images.
References Cited (Backward Citations)
US3566669A
Cited
GB2125556A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1990-02-16 | 1990-08-18 | 1991-02-17 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1994-02-16 | 1994-08-18 | 1995-02-17 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1998-02-16 | 1998-08-18 | 1999-02-17 | $7700.00 | Window Closed / Lapsed |